XFOIL Version 6.96 Calculated polar for: TH 25816 HALE AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.500 -0.2014 0.08750 0.08427 -0.1808 0.9166 0.0237 -17.250 -0.2301 0.08073 0.07735 -0.1834 0.9152 0.0236 -17.000 -0.2554 0.07420 0.07067 -0.1856 0.9143 0.0233 -16.750 -0.2752 0.06831 0.06463 -0.1876 0.9135 0.0231 -16.500 -0.2994 0.06212 0.05825 -0.1891 0.9128 0.0229 -16.250 -0.3192 0.05644 0.05236 -0.1900 0.9121 0.0225 -16.000 -0.3328 0.05168 0.04742 -0.1909 0.9115 0.0225 -15.750 -0.3442 0.04710 0.04263 -0.1914 0.9110 0.0224 -15.500 -0.3686 0.04470 0.04010 -0.1865 0.9041 0.0222 -15.250 -0.3772 0.04136 0.03658 -0.1854 0.9016 0.0223 -15.000 -0.3755 0.03819 0.03323 -0.1853 0.9003 0.0221 -14.750 -0.3699 0.03534 0.03022 -0.1856 0.8995 0.0221 -14.500 -0.3591 0.03264 0.02734 -0.1860 0.8988 0.0221 -14.250 -0.3468 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0.7295 0.7568 0.250 0.3337 0.01308 0.00774 -0.0840 0.7282 0.7585 0.500 0.3299 0.01348 0.00820 -0.0780 0.7244 0.7616 0.750 0.3292 0.01382 0.00857 -0.0728 0.7205 0.7651 1.000 0.3506 0.01391 0.00865 -0.0722 0.7181 0.7685 1.250 0.3797 0.01390 0.00859 -0.0732 0.7162 0.7716 1.500 0.4126 0.01389 0.00857 -0.0748 0.7148 0.7736 1.750 0.4497 0.01385 0.00852 -0.0773 0.7134 0.7753 2.000 0.4888 0.01384 0.00849 -0.0802 0.7121 0.7772 2.250 0.5304 0.01387 0.00849 -0.0836 0.7107 0.7791 2.500 0.4887 0.01471 0.00944 -0.0703 0.7048 0.7844 2.750 0.5036 0.01491 0.00962 -0.0685 0.7018 0.7883 3.000 0.5305 0.01496 0.00969 -0.0689 0.6998 0.7905 3.250 0.5637 0.01495 0.00969 -0.0705 0.6982 0.7924 3.500 0.6002 0.01492 0.00965 -0.0729 0.6969 0.7944 3.750 0.6391 0.01488 0.00960 -0.0757 0.6956 0.7964 4.000 0.6809 0.01486 0.00956 -0.0792 0.6943 0.7986 4.250 0.6302 0.01599 0.01078 -0.0645 0.6871 0.8051 4.500 0.6485 0.01617 0.01100 -0.0633 0.6843 0.8075 4.750 0.6793 0.01616 0.01101 -0.0644 0.6824 0.8095 5.000 0.7157 0.01608 0.01092 -0.0667 0.6809 0.8115 5.250 0.7552 0.01596 0.01080 -0.0696 0.6795 0.8135 5.500 0.7979 0.01584 0.01067 -0.0732 0.6780 0.8157 5.750 0.7476 0.01720 0.01212 -0.0590 0.6702 0.8222 6.000 0.7696 0.01727 0.01221 -0.0585 0.6672 0.8246 6.250 0.8036 0.01713 0.01209 -0.0603 0.6652 0.8264 6.500 0.8426 0.01692 0.01189 -0.0630 0.6635 0.8281 6.750 0.8852 0.01671 0.01168 -0.0664 0.6617 0.8300 7.000 0.8421 0.01816 0.01324 -0.0538 0.6541 0.8355 7.250 0.8645 0.01825 0.01333 -0.0536 0.6506 0.8391 7.500 0.9014 0.01797 0.01304 -0.0559 0.6482 0.8414 7.750 0.9414 0.01765 0.01273 -0.0587 0.6459 0.8429 8.000 0.9185 0.01878 0.01395 -0.0500 0.6391 0.8462 8.250 0.9297 0.01911 0.01432 -0.0476 0.6342 0.8491 8.500 0.9639 0.01887 0.01407 -0.0494 0.6310 0.8518 8.750 1.0087 0.01843 0.01362 -0.0531 0.6282 0.8543 9.000 0.9719 0.02009 0.01537 -0.0425 0.6196 0.8591 9.250 0.9955 0.02001 0.01530 -0.0423 0.6147 0.8611 9.500 1.0143 0.02016 0.01547 -0.0413 0.6092 0.8633 9.750 1.0008 0.02137 0.01675 -0.0349 0.6009 0.8668 10.000 1.0321 0.02114 0.01650 -0.0362 0.5960 0.8695 10.250 1.0156 0.02269 0.01810 -0.0298 0.5860 0.8737 10.500 1.0396 0.02264 0.01804 -0.0298 0.5795 0.8761 10.750 1.0238 0.02416 0.01964 -0.0234 0.5692 0.8790 11.000 1.0476 0.02414 0.01959 -0.0234 0.5621 0.8812 11.250 1.0353 0.02577 0.02129 -0.0180 0.5503 0.8845 11.500 1.0429 0.02660 0.02212 -0.0158 0.5401 0.8874 11.750 1.0539 0.02734 0.02285 -0.0143 0.5298 0.8902 12.000 1.0514 0.02857 0.02410 -0.0106 0.5167 0.8928 12.250 1.0535 0.02961 0.02515 -0.0075 0.5038 0.8952 12.500 1.0571 0.03065 0.02616 -0.0049 0.4895 0.8977 12.750 1.0572 0.03195 0.02742 -0.0019 0.4725 0.9003 13.000 1.0600 0.03319 0.02861 0.0005 0.4567 0.9029 13.250 1.0605 0.03466 0.03002 0.0031 0.4398 0.9052 13.500 1.0589 0.03606 0.03138 0.0061 0.4225 0.9075 13.750 1.0561 0.03759 0.03286 0.0092 0.4060 0.9097 14.000 1.0546 0.03914 0.03436 0.0119 0.3890 0.9120 14.250 1.0522 0.04085 0.03602 0.0146 0.3722 0.9142 14.500 1.0517 0.04252 0.03764 0.0168 0.3555 0.9164 14.750 1.0487 0.04445 0.03951 0.0192 0.3372 0.9186 15.000 1.0485 0.04624 0.04125 0.0211 0.3206 0.9204 15.250 1.0464 0.04801 0.04298 0.0234 0.3051 0.9223 15.500 1.0452 0.04980 0.04473 0.0255 0.2888 0.9243 15.750 1.0432 0.05174 0.04662 0.0275 0.2731 0.9264 16.000 1.0431 0.05360 0.04843 0.0291 0.2578 0.9284 16.250 1.0431 0.05557 0.05036 0.0306 0.2427 0.9304 16.750 1.0452 0.05951 0.05421 0.0329 0.2128 0.9338 17.000 1.0463 0.06135 0.05602 0.0342 0.1991 0.9357 17.250 1.0450 0.06346 0.05809 0.0355 0.1843 0.9377 17.500 1.0474 0.06536 0.05996 0.0364 0.1741 0.9396 17.750 1.0473 0.06755 0.06211 0.0373 0.1623 0.9414 18.000 1.0503 0.06955 0.06410 0.0379 0.1510 0.9432 18.250 1.0543 0.07148 0.06602 0.0384 0.1415 0.9450 18.500 1.0542 0.07385 0.06836 0.0389 0.1328 0.9465 18.750 1.0605 0.07563 0.07016 0.0391 0.1251 0.9483 19.000 1.0618 0.07792 0.07245 0.0394 0.1187 0.9499 19.250 1.0684 0.07974 0.07430 0.0394 0.1127 0.9517